Tandem air cycle machine module for environmental control systems

ABSTRACT

Tandem air cycle machine modules include a first air cycle machine having a first compressor and a first turbine, a second air cycle machine having a second compressor and a second turbine, and a structural manifold operably connected to both the first air cycle machine and the second air cycle machine.

CROSS-REFERENCE TO RELATED APPLICATIONS

The present application claims priority from U.S. Provisional PatentApplication Numbers 62/309,076, 62/309,080, 62/309,081, and 62/309,084,filed on Mar. 16, 2016. The contents of the priority applications arehereby incorporated by reference in their entireties.

BACKGROUND

The subject matter disclosed herein generally relates to environmentalcontrol systems and, more particularly, to air cycle machines ofenvironmental control systems.

Commercial aircraft are conventionally equipped with two-packenvironmental control system architectures that include redundant packsinstalled in separate bays beneath a center wing box of the aircraft andare encapsulated by the aircraft wing-to-body fairing. These bays arecommonly separated by a Keel Beam that supports the weight of theaircraft in the event of a wheels-up landing. Local penetrations of thekeel beam can be accommodated if properly reinforced.

Smaller configurations of environmental control system architectures caninclude pack-and-a-half architectures that fit within a single volume.However, such volume is larger than half of the convention two-packarchitectures, and thus the pack-and-a-half architecture systems may betoo large for use in such locations, and thus may be required to beinstalled in other locations of the aircraft (e.g., in a tail cone ofthe aircraft). It may be beneficial to further reduce the size ofpack-and-a-half environmental control system architectures.

SUMMARY

According to one embodiment, a tandem air cycle machine module isprovided. The tandem air cycle machine module includes a first air cyclemachine having a first compressor and a first turbine, a second aircycle machine having a second compressor and a second turbine, and astructural manifold operably connected to both the first air cyclemachine and the second air cycle machine.

In addition to one or more of the features described above, or as analternative, further embodiments of the tandem air cycle machine modulemay include an isolation valve within the structural manifold andconfigured to control an airflow into the first turbine and the secondturbine.

In addition to one or more of the features described above, or as analternative, further embodiments of the tandem air cycle machine modulemay include that the isolation valve comprises an actuator and a gate,the actuator configured to control and move the gate to selectivelyblock flow into the first turbine or the second turbine.

In addition to one or more of the features described above, or as analternative, further embodiments of the tandem air cycle machine modulemay include that the isolation valve further comprises a cover thatfixedly connects to the structural manifold, the gate movably mounted tothe cover.

In addition to one or more of the features described above, or as analternative, further embodiments of the tandem air cycle machine modulemay include that the isolation valve is operable into (i) a firstposition wherein airflow can enter both the first turbine and the secondturbine, (ii) a second position wherein airflow can enter only the firstturbine and is prevented from entering the second turbine, and (iii) athird position wherein airflow can enter only the second turbine and isprevented from entering the first turbine.

In addition to one or more of the features described above, or as analternative, further embodiments of the tandem air cycle machine modulemay include that the structural manifold includes a manifold inletconfigured to receive an airflow from a water collector of anenvironmental control system of an aircraft.

In addition to one or more of the features described above, or as analternative, further embodiments of the tandem air cycle machine modulemay include at least one mounting pad on the structural manifold, the atleast one mounting pad configured to mount the structural manifold to astructure of an aircraft.

In addition to one or more of the features described above, or as analternative, further embodiments of the tandem air cycle machine modulemay include at least one vibration isolator configured to limittransmission of vibration to or from the tandem air cycle machine.

In addition to one or more of the features described above, or as analternative, further embodiments of the tandem air cycle machine modulemay include a plurality of securing mechanisms that connect and secureattachment of the first and second air cycle machines to the structuralmanifold.

According to another embodiment, an environmental control system of anaircraft is provided. The environmental control system includes a tandemair cycle machine module having a first air cycle machine having a firstcompressor and a first turbine, a second air cycle machine having asecond compressor and a second turbine, and a structural manifoldoperably connected to both the first air cycle machine and the secondair cycle machine.

In addition to one or more of the features described above, or as analternative, further embodiments of the environmental control system mayinclude an isolation valve within the structural manifold and configuredto control an airflow into the first turbine and the second turbine.

In addition to one or more of the features described above, or as analternative, further embodiments of the environmental control system mayinclude that the isolation valve comprises an actuator and a gate, theactuator configured to control and move the gate to selectively blockflow into the first turbine or the second turbine.

In addition to one or more of the features described above, or as analternative, further embodiments of the environmental control system mayinclude that the isolation valve further comprises a cover that fixedlyconnects to the structural manifold, the gate movably mounted to thecover.

In addition to one or more of the features described above, or as analternative, further embodiments of the environmental control system mayinclude that the isolation valve is operable into (i) a first positionwherein airflow can enter both the first turbine and the second turbine,(ii) a second position wherein airflow can enter only the first turbineand is prevented from entering the second turbine, and (iii) a thirdposition wherein airflow can enter only the second turbine and isprevented from entering the first turbine.

In addition to one or more of the features described above, or as analternative, further embodiments of the environmental control system mayinclude that the structural manifold includes a manifold inletconfigured to receive an airflow from a water collector of anenvironmental control system of an aircraft.

In addition to one or more of the features described above, or as analternative, further embodiments of the environmental control system mayinclude at least one mounting pad on the structural manifold, the atleast one mounting pad configured to mount the structural manifold to astructure of an aircraft.

In addition to one or more of the features described above, or as analternative, further embodiments of the environmental control system mayinclude at least one vibration isolator configured to limit transmissionof vibration to or from the tandem air cycle machine.

In addition to one or more of the features described above, or as analternative, further embodiments of the environmental control system mayinclude a plurality of securing mechanisms that connect and secureattachment of the first and second air cycle machines to the structuralmanifold.

In addition to one or more of the features described above, or as analternative, further embodiments of the environmental control system mayinclude a water collector configured to supply conditioned air to thestructural manifold.

In addition to one or more of the features described above, or as analternative, further embodiments of the environmental control system mayinclude a ram module, the ram module configured to receive air from atleast one of the first compressor and the second compressor.

Technical effects of embodiments of the present disclosure includetandem air cycle machine modules for environmental control systemarchitectures that include two or more air cycle machines operablycoupled to a single central structural manifold. Further technicaleffects include air cycle machine isolation valves configured to controlflow into and through tandem air cycle machine modules of the presentdisclosure.

The foregoing features and elements may be combined in variouscombinations without exclusivity, unless expressly indicated otherwise.These features and elements as well as the operation thereof will becomemore apparent in light of the following description and the accompanyingdrawings. It should be understood, however, that the followingdescription and drawings are intended to be illustrative and explanatoryin nature and non-limiting.

BRIEF DESCRIPTION OF THE DRAWINGS

The subject matter is particularly pointed out and distinctly claimed atthe conclusion of the specification. The foregoing and other features,and advantages of the present disclosure are apparent from the followingdetailed description taken in conjunction with the accompanying drawingsin which:

FIG. 1A is a schematic illustration of an aircraft that can incorporatevarious embodiments of the present disclosure;

FIG. 1B is a schematic illustration of a bay section of the aircraft ofFIG. 1A;

FIG. 2A is a schematic, perspective illustration of an environmentalcontrol system of an aircraft that can incorporate embodiments of thepresent disclosure;

FIG. 2B is a second perspective illustration of the environmentalcontrol system of FIG. 2A;

FIG. 3 is a schematic diagram of an environmental control system inaccordance with an embodiment of the present disclosure;

FIG. 4A is a schematic illustration of a tandem air cycle machine modulein accordance with an embodiment of the present disclosure as assembled;

FIG. 4B is a partially exploded illustration of the tandem air cyclemachine module of FIG. 4A;

FIG. 5A is an isometric exploded schematic illustration of a structuralmanifold in accordance with an embodiment of the present disclosure;

FIG. 5B is an alternative view isometric exploded schematic illustrationof the structural manifold of FIG. 5A;

FIG. 6A is a schematic illustration of an isolation valve in accordancewith an embodiment of the present disclosure in a first position;

FIG. 6B is a schematic illustration of the isolation valve of FIG. 6A ina second position;

FIG. 6C is a schematic illustration of the isolation valve of FIG. 6A ina third position; and

FIG. 7 is a cross-sectional illustration of a structural manifold inaccordance with an embodiment of the present disclosure.

DETAILED DESCRIPTION

As shown and described herein, various features of the disclosure willbe presented. Various embodiments may have the same or similar featuresand thus the same or similar features may be labeled with the samereference numeral, but preceded by a different first number indicatingthe figure to which the feature is shown. Thus, for example, element“##” that is shown in FIG. X may be labeled “X##” and a similar featurein FIG. Z may be labeled “Z##.” Although similar reference numbers maybe used in a generic sense, various embodiments will be described andvarious features may include changes, alterations, modifications, etc.as will be appreciated by those of skill in the art, whether explicitlydescribed or otherwise would be appreciated by those of skill in theart.

As shown in FIGS. 1A-1B, an aircraft 101 can include one or more bays103 beneath a center wing box. The bay 103 can contain and/or supportone or more components of the aircraft 101. For example, in someconfigurations, the aircraft 101 can include environmental controlsystems within the bay 103. As shown in FIG. 1B, the bay 103 includesbay doors 105 that enable installation and access to one or morecomponents (e.g., environmental control systems). During operation ofenvironmental control systems, air that is external to the aircraft 101can flow into one or more environmental control systems within the baydoors 105 through one or more ram air inlets 107. The air may then flowthrough the environmental control systems to be processed and suppliedto various components or locations within the aircraft 101 (e.g.,passenger cabin, etc.). Some air may be exhaust through one or more ramair exhaust outlets 109.

Turning now to FIGS. 2A-2B, an environmental control system 200 inaccordance with an embodiment of the present disclosure is shown. Theenvironmental control system 200 includes a ram module 202 and arefrigeration module 204 that are operably connected by one or moreducts 206 a, 206 b, 206 c. FIG. 2A shows a first perspectiveillustration of the environmental control system 200 and FIG. 2B shows asecond perspective illustration of the environmental control system 200.The environmental control system 200 of FIGS. 2A-2B is merely forillustrative and explanatory purposes, and those of skill in the artwill appreciate that various embodiments of the present disclosure canbe configured with different types of environmental control systemsand/or different configurations of environmental control systems, andthus, the present discussion and associated illustrations are notintended to be limiting.

As shown, in FIGS. 2A-2B, the ram module 202 includes a primary heatexchanger 208 a and a secondary heat exchanger 208 b. The heatexchangers 208 a, 208 b are configured to receive ram air A_(ram) andbleed air A_(bleed) to condition air within the ram module 202. The rammodule 202 further includes a ram outlet header 210 and a ram exhaustheader 212. Located between the headers 210, 212 may be one or more ramfans 214. Air from the ram module 202 can be conveyed to or from therefrigeration module 204 through the ducts 206 a, 206 b, 206 c.

The refrigeration module 204 includes a condenser heat exchanger 216 andone or more air cycle machines 218. The condenser heat exchanger 216 canbe operably connected to the secondary heat exchanger 208 b by a firstduct 206 a that can supply hot air to the condenser heat exchanger 216.The air cycle machines 218 can be connected to one or both of the heatexchangers 208 a, 208 b, as shown. Recirculated air A_(recirc) can besupplied to and mixed with turbine outlet air from the air cyclemachines 218 as indicated in FIG. 2A.

The condenser heat exchanger 216 is configured to condition air andsupply relatively cool or cold air A_(cabin) to a cabin of an aircraft.Thus, the condenser heat exchanger 216 includes an outlet header 220.The hot air that is supplied to the condenser heat exchanger 216 throughthe duct 206 a is fed into an inlet header 222 of the condenser heatexchanger 216.

As shown in FIGS. 2A-2B, the ram fans 214 and the air cycle machines 218are separated. Such a configuration enables the separation of theenvironmental control system 200 to be separated into the ram module 202and the refrigeration module 204. As shown, the ram module 202 includesthe ram fans 214. In some embodiments, the ram fans 214 can beconfigured as dual electric ram fans that can provide a required ramcooling performance and redundancy. The ram fans 214 can be operatedseparately or at the same time to enable control and variance in ramflow. Fixed speed fans, two speed fans, or variable speed fans can beused without departing from the scope of the present disclosure.Accordingly, the environmental control system 200 can be installed intotwo separate volumes on an aircraft (e.g., in two separate bays) ascompared to a single large volume.

For example, turning now to FIG. 3, a schematic diagram of anenvironmental control system 300 in accordance with an embodiment of thepresent disclosure is shown. The environmental control system 300 may besimilar to that shown and described in FIGS. 2A-2B, and thus likefeatures will not be described again.

The environmental control system 300 includes a ram module 302 and arefrigeration module 304. In some configurations, when installed on anaircraft, the ram module 302 can be installed into a right-hand side ofthe aircraft, and thus through a first bay door and the refrigerationmodule 304 can be installed into a left-hand side of the aircraft, andthrough a second bay door. In FIG. 3, an aircraft centerline 311 isindicated as separating the ram module 302 from the refrigeration module304.

The ram module 302 is operably connected to the refrigeration module 304by one or more ducts 306 a, 306 b, 306 c. The environmental controlsystem 300 includes a primary heat exchanger 308 a and a secondary heatexchanger 308 b that receive bleed air A_(bleed) and ram air A_(ram),respectively, to condition air within the ram module 302. One or moreram fans 314 are configured to aid in exhausting ram exhaust air A_(ram)_(_) _(exhaust) from the ram module 302.

As shown, the refrigeration module 304 includes a condenser heatexchanger 316 and tandem air cycle machines 318 a, 318 b. Each of thetandem air cycle machines 318 a, 318 b includes a respective compressor324 a, 324 b and a respective turbine 326 a, 326 b. The tandem air cyclemachines 318 a, 318 b can form a tandem air cycle machine module 328, asindicated by the dashed-line box in FIG. 3. The tandem air cycle machinemodule 328 can include two air cycle machines (e.g., 318 a, 318 b) thatare operably connected to a centralized manifold, as described herein,and thus form a compact, unitized assembly. Although shown and describedherein with two air cycle machines 318 a, 318 b, those of skill in theart will appreciate that embodiments of the present disclosure can beapplied to two, three, or four wheel tandem air cycle machines. Asshown, a water collector 329 is configured to extract moisture from airof the condenser 316 and supply the conditioned air to the air cyclemachines 318 a, 318 b. An air cycle machine isolation valve 332 isschematically shown that is configured to be operated and control fluidflow into one or both of the air cycle machines 318 a, 318 b.

Turning now to FIGS. 4A-4B, schematic illustrations of a tandem aircycle machine module 428 in accordance with an embodiment of the presentdisclosure are shown. FIG. 4A illustrates the tandem air cycle machinemodule 428 as assembled and FIG. 4B illustrates the tandem air cyclemachine module 428 in a partially exploded view.

As shown in FIGS. 4A, the tandem air cycle machine module 428 includes afirst air cycle machine 418 a and a second air cycle machine 418 b. Theair cycle machines 418 a, 418 b include respective compressors 424 a,424 b and respective turbines 426 a, 426 b. As shown, the first andsecond air cycle machines 418 a, 418 b are operably connected by acentral structural manifold 430. As described herein, an isolation valve432 can be configured within the structural manifold 430 and configuredto air flow into one or both of the air cycle machines 418 a, 418 b.

Further, as shown in FIG. 4A, the tandem air cycle machine module 428includes one or more vibration isolators 434 that are configured toenable mounting of the tandem air cycle machine module 428 to anaircraft and provide vibration protection to the tandem air cyclemachine module 428.

As shown in FIG. 4B, the second air cycle machine 418 b is shownseparated from the structural manifold 430. In the exploded view of FIG.4B, the connections between the air cycle machine 418 b and thestructural manifold 430 are shown. The air cycle machine 418 b includestwo ACM connectors 436 and the structural manifold 430 includes twocorresponding manifold connectors 438. The connectors 436, 438 can befixed by securing mechanisms 440. The securing mechanisms 440 can beC-clamps, D-clamps, flanges, fasteners, or other devices or structuresused to secure components together. In some embodiments, the securingmechanisms can be formed as interference fits between the respectiveconnectors 436, 438.

Turning now to FIGS. 5A-5B, exploded view, schematic illustrations of astructural manifold 530 in accordance with an embodiment of the presentdisclosure are shown. The structural manifold 530 includes an air cyclemachine isolation valve 532 that is configured to control airflow from awater collector to one or both of the air cycle machines of a tandem aircycle machine module. Air can enter the structural manifold 530 at amanifold inlet 542. Air within the structural manifold 530 can bedirected to a first air cycle machine through a first compressor outlet544 a, a second compressor outlet 544 b, a first turbine inlet 546 a, asecond turbine inlet 546 b, or a compressor outlet 547. As will beappreciated by those of skill in the art, the first compressor outlet544 a and the first turbine inlet 546 a can fluidly connector to a firstair cycle machine and the second compressor outlet 544 b and the secondturbine inlet 546 b can fluidly connector to a second air cycle machine(e.g., as shown and described above).

The isolation valve 532 is configured within the manifold 530 includes agate 548, a cover 550, an actuator 552, and a fastening mechanism 554.The actuator 552 is mounted to the cover 550 and is configured tocontrol (e.g., rotate, open/close, etc.) the gate 548. The fasteningmechanism 554, as shown, comprises multiple fasteners, though those ofskill in the art will appreciate that any type of fastening can be usedwithout departing from the scope of the present disclosure. For example,in some embodiments, the fastening mechanism can be achieved by welding,adhesives, interference fits, etc. The gate 548 of the isolation valve532 is moveable or actuatable to selectively block flow through theturbine inlets 546 a, 546 b. The gate 548, as shown in the embodiment ofFIGS. 5A-5B, is rotatably mounted on the cover 550 and within themanifold 530.

A first position of the gate 548, as controlled by the actuator 552, canbe a position such that neither the first turbine inlet 546 a nor thesecond turbine inlet 546 b are blocked. That is, in the first position,airflow can flow into both a first turbine and a second turbine of atandem air cycle machine module. In a second position, the gate 548moved or positioned to block the second turbine inlet 546 b and flow isallowed to flow through the first turbine inlet 546 a. In a thirdposition, the gate 548 is moved or positioned to block the first turbineinlet 546 a and flow is allowed to flow through the second turbine inlet546 b.

Also shown in FIGS. 5A-5B, the structural manifold 530 can include oneor more mounting pads 556. The mounting pads 556 are configured toenable the structural manifold 530 to be mounted to an aircraft or otherstructure. In some embodiments, the mounting pads 556 can be configuredto mount or receive vibration isolators that are then used for mountingto an aircraft or other structure.

Turning now to FIGS. 6A-6C, first, second, and third positions of anisolation valve 632 in accordance with an embodiment of the presentdisclosure are shown. FIG. 6A illustrates the isolation valve 632 in thefirst position, FIG. 6B illustrates the isolation valve 632 in thesecond position, and FIG. 6C illustrates the isolation valve 632 in thethird position. The isolation valve 632 of FIGS. 6A-6C is similar tothat shown and described above. That is, the isolation valve 632 isconfigured within a tandem air cycle machine module 628 between a firstair cycle machine 618 a and a second air cycle machine 618 b. Theisolation valve 632 is configured within and part of a structuralmanifold 630 and is operable to control flow from manifold inlet 642into and through a first turbine inlet 646 a and a second turbine inlet646 b. The first and second turbine inlets 646 a, 646 b of the manifold630 are fluid passages into a first turbine 626 a and second turbine 626b of respective first air cycle machine 618 a and second air cyclemachine 618 b of the tandem air cycle machine module 628.

As noted, FIG. 6A illustrates the isolation valve 632 in the firstposition. As shown, a valve gate 648 is configured such that it does notblock or otherwise obstruct fluid flow through either of the firstturbine inlet 646 a or the second turbine inlet 646 b. The flow isillustrated by the arrows in FIG. 6A, with flow entering the manifold630 from the inlet 642 and flowing into both the first turbine 626 a andthe second turbine 626 b.

FIG. 6B, shows the isolation valve 632 in a second position, wherein thegate 648 is configured and positioned to block flow into the secondturbine 626 b and covers or obstructs the second turbine inlet 646 b. Asshown in FIG. 6B, the arrows illustrate a fluid flow path, andparticular illustrate that air flow is only conveyed into the firstturbine 626 a through the first turbine inlet 646 a.

FIG. 6C, shows the isolation valve 632 in a third position, wherein thegate 648 is configured and positioned to block flow into the firstturbine 626 a and covers or obstructs the first turbine inlet 646 a. Asshown in FIG. 6C, the arrows illustrate a fluid flow path, andparticular illustrate that air flow is only conveyed into the secondturbine 626 b through the second turbine inlet 646 b.

Turning now to FIG. 7, a cross-sectional illustration of a structuralmanifold 730 of a tandem air cycle machine module in accordance with anembodiment of the present disclosure is shown. The structural manifold730 may be similar to that shown and described above and includes amanifold inlet 742 that allows fluid flow into the manifold 730. Fluidcan then exit the manifold 730 through a first turbine inlet 746 a (asecond turbine inlet is not shown based on the cross-sectional view).Further, as shown, the structural manifold 730 includes a firstcompressor outlet 744 a and a second compressor inlet 744 b throughwhich air can flow through a compressor outlet 747. FIG. 7 alsoillustrates a bulkhead 758 that can provide structural integrity and/orstability to the manifold 730. Further, as shown, the bulkhead 758 caninclude a valve support 760 integrally formed therein. The valve support760 can receive a portion of an isolation valve (e.g., a portion of agate of the valve).

Advantageously, embodiments described herein provide tandem air cyclemachine modules having two air cycle machines and a centralized manifoldto form a compact unitized assembly. Various embodiments can be appliedto, for example, two, three, or four wheel tandem air cycle machines. Insome embodiments, an isolation valve can be integrated into thecentralized manifold and control airflow into one or more of theconnected air cycle machines. In accordance with some embodiments of thepresent disclosure, the central, shared manifold can simplify systemducting arrangements by coupling turbine inlet and compressor outletconnections. Furthermore, in some embodiments, a number of mountingpoints can simplify attachment to aircraft while facilitating theremoval and replacement of individual air cycle machines of the tandemair cycle machine module. That is, embodiments provided herein enable amodule and separable system wherein various parts or components can beseparately removed and/or replaced during maintenance operations.Moreover, in some embodiments, vibration isolators can limit thetransmission of structural borne noise to the airframe as well asexternal loads transmitted to the air cycle machines of the tandem aircycle machine module.

The use of the terms “a,” “an,” “the,” and similar references in thecontext of description (especially in the context of the followingclaims) are to be construed to cover both the singular and the plural,unless otherwise indicated herein or specifically contradicted bycontext. The modifier “about” used in connection with a quantity isinclusive of the stated value and has the meaning dictated by thecontext (e.g., it includes the degree of error associated withmeasurement of the particular quantity). All ranges disclosed herein areinclusive of the endpoints, and the endpoints are independentlycombinable with each other. It should be appreciated that relativepositional terms such as “forward,” “aft,” “upper,” “lower,” “above,”“below,” and the like are with reference to normal operational attitudeand should not be considered otherwise limiting.

While the present disclosure has been described in detail in connectionwith only a limited number of embodiments, it should be readilyunderstood that the present disclosure is not limited to such disclosedembodiments. Rather, the present disclosure can be modified toincorporate any number of variations, alterations, substitutions,combinations, sub-combinations, or equivalent arrangements notheretofore described, but which are commensurate with the scope of thepresent disclosure. Additionally, while various embodiments of thepresent disclosure have been described, it is to be understood thataspects of the present disclosure may include only some of the describedembodiments.

For example, although shown and described with respect to a tandem aircycle machine module having two air cycle machines, various other tandemair cycle machine modules may employ embodiments of the presentdisclosure. For example, embodiments provided herein can be applied totwo, three, or four wheel tandem air cycle machines.

Accordingly, the present disclosure is not to be seen as limited by theforegoing description, but is only limited by the scope of the appendedclaims.

What is claimed is:
 1. A tandem air cycle machine module comprising: a first air cycle machine having a first compressor and a first turbine; a second air cycle machine having a second compressor and a second turbine; and a structural manifold operably connected to both the first air cycle machine and the second air cycle machine.
 2. The tandem air cycle machine module of claim 1, further comprising an isolation valve within the structural manifold and configured to control an airflow into the first turbine and the second turbine.
 3. The tandem air cycle machine module of claim 2, wherein the isolation valve comprises an actuator and a gate, the actuator configured to control and move the gate to selectively block flow into the first turbine or the second turbine.
 4. The tandem air cycle machine module of claim 3, the isolation valve further comprising a cover that fixedly connects to the structural manifold, the gate movably mounted to the cover.
 5. The tandem air cycle machine module of claim 2, wherein the isolation valve is operable into (i) a first position wherein airflow can enter both the first turbine and the second turbine, (ii) a second position wherein airflow can enter only the first turbine and is prevented from entering the second turbine, and (iii) a third position wherein airflow can enter only the second turbine and is prevented from entering the first turbine.
 6. The tandem air cycle machine module of claim 1, wherein the structural manifold includes a manifold inlet configured to receive an airflow from a water collector of an environmental control system of an aircraft.
 7. The tandem air cycle machine module of claim 1, further comprising at least one mounting pad on the structural manifold, the at least one mounting pad configured to mount the structural manifold to a structure of an aircraft.
 8. The tandem air cycle machine module of claim 1, further comprising at least one vibration isolator configured to limit transmission of vibration to or from the tandem air cycle machine.
 9. The tandem air cycle machine module of claim 1, further comprising a plurality of securing mechanisms that connect and secure attachment of the first and second air cycle machines to the structural manifold.
 10. An environmental control system of an aircraft, the environmental control system comprising: a tandem air cycle machine module comprising: a first air cycle machine having a first compressor and a first turbine; a second air cycle machine having a second compressor and a second turbine; and a structural manifold operably connected to both the first air cycle machine and the second air cycle machine.
 11. The environmental control system of claim 10, further comprising an isolation valve within the structural manifold and configured to control an airflow into the first turbine and the second turbine.
 12. The environmental control system of claim 11, wherein the isolation valve comprises an actuator and a gate, the actuator configured to control and move the gate to selectively block flow into the first turbine or the second turbine.
 13. The environmental control system of claim 12, the isolation valve further comprising a cover that fixedly connects to the structural manifold, the gate movably mounted to the cover.
 14. The environmental control system of claim 11, wherein the isolation valve is operable into (i) a first position wherein airflow can enter both the first turbine and the second turbine, (ii) a second position wherein airflow can enter only the first turbine and is prevented from entering the second turbine, and (iii) a third position wherein airflow can enter only the second turbine and is prevented from entering the first turbine.
 15. The environmental control system of claim 10, wherein the structural manifold includes a manifold inlet configured to receive an airflow from a water collector of an environmental control system of an aircraft.
 16. The environmental control system of claim 10, further comprising at least one mounting pad on the structural manifold, the at least one mounting pad configured to mount the structural manifold to a structure of an aircraft.
 17. The environmental control system of claim 10, further comprising at least one vibration isolator configured to limit transmission of vibration to or from the tandem air cycle machine.
 18. The environmental control system of claim 10, further comprising a plurality of securing mechanisms that connect and secure attachment of the first and second air cycle machines to the structural manifold.
 19. The environmental control system of claim 10, further comprising a water collector configured to supply conditioned air to the structural manifold.
 20. The environmental control system of claim 10, further comprising a ram module, the ram module configured to receive air from at least one of the first compressor and the second compressor. 